FILING INSTRUCTIONS:

REASON FOR ISSUE: 

### Maintenance Manual TEMPORARY REVISION
TEMPORARY REVISION TR330-AMM-36

Insert this TR before Ghapter 5-20-02, page 1. Microfiche holders of the 503-30 Aircraft Maintenance Manual should insert this Temporary Revision atthe front of their microfiche folder.
1. A critical design configuration control limitation (GOGCl) definition is introduced. 2. Additional COGCl's have been identified associated with preservation of fuel tank system ignition prevention design features when assessed against the EASNF AA harmonised cmeria. 3. Notes related to application of GOGGl's are introduced. 4. All other information is introduced as a consequence of completing the system safety review required by EASA INT/POU25/12 (and hence SFAR 88).

NOTE: Record the incorporation of this Temporary Revision on the yellow RECORD OF TEMPORARY REVISIONS sheet at the front of the Manual.
The technical content of this document is approved under the authority of OOA No. EASA.21 J.068.

Signed

. Date

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# 5-20-02 TR330-AMM-36 Page 1 of3 Jun 

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# SHORTSEiC Maintenance 

# CQJo

# C?Jrij1 Manual ~ 

# e?J~ TEMPORARY REVISION FUEL SYSTEM CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION


### 1. General
COCel's (Critical Design Control Configuration Limitations) are Fuel System Airworthiness Limitations that are a means of identifying certain design configuration features intended to preclude afuel tank ignition source for the operational life of the airplane. GOGeL's are mandatory and cannot be changed or deleted without the approval of the European Aviation Safety Agency (EASA), or the national regulatory authority office that is responsible for the SD3 Type Certificate.
A critical fuel tank ignition source prevention feature may exist in the fuel system and its related installation, or in systems that, 

### if a failure condition were to develop, could interact with the fuel system in such away that an unsafe condition would develop without this limitation. Strict adherence to configuration, methods, techniques and practices as prescribed below is required to ensure the 

### COCCl is complied with. Any use of parts, methods, techniques or practices not contained in the applicable 

### COCCl requires approval by the European Aviation Safety Agency (EASA), or the national regulatory authority office that is responsible for the S03 Type Certificate.
The purpose of the 

### GOGGl, isto provide instructions to retain a critical ignition source prevention feature during configuration change, that may be caused by modifications, repairs, or maintenance actions.

ITEM A Float switch assemblies

8 Fuel contents gauging

C FCGS ca.-axialcable assemblies NOTE Field maintenance offioat switches isnot permissible. There are internal design features which arecritical tofueltank safety. The units must be maintained inaccordance with the original equipment manufacturer (OEM) overhaul manual (section 28--41-65),by appropriately approved maintenance organisations. Routing ofany additional electrical power/signal cables is not permitted within six inches ofthefuel contents gauging system (FCGS) co-axial cables, extemal tothefuel tanks. Referto 28A-42-02 or288-42-02, Figure 201 (respective Preor Post Mod 6738 aircraft). Itisnot permissible to route any additional electrical power/signal cables within thefuel tank. Itisnot permissible to clip/attach any additional electrical power/ signal cables tothe outside surfaces ofthe fuel tank, ortofuel pipes. 11isimportant to assure the physical condition ofthe hamess cables, which the FCGS co~axialcable assemblies are routed within. When performing maintenance or incorporating design change, all cables must be adequately protected against accidental damage, including swarf penetration. Cables must be inspected following completion ofwork, to ensure that nodamage has occurred and noswarf material has contaminated the harness. Referto 28A-42-02 or288-42-02, pb201 and28A-42-03 or288-42-03, pb201 (respective Preor Post Mod 6738 aircraft). RepairofFCGS co-axial cable assemblies isnot permitted: they must bereplaced (refer to20-09-13, pb201).



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# ~@[Q] Maintenance Manual TEMPORARY REVISION

D



### E ITEM Fueltankexternal bonding leads

Fuel tank internal bonding leads and cables NOTE Ifdisturbed and/or disassembled, the bonding leads onthe fuel vent pipes atthe external forward and afttank interfaces must undergo a detailed visual inspection (DVI), after re-assembly (referto 20·09-05, pb201). After all internal·to-tank maintenance, itisimportant to make sure that bothfuel vent system bonding leads in cell 2oftheforward fuei tank have not been disturbed. These bonding leads musl notfoul adjacent pipes/structure and thesecurity oftheir attachment must be confirmed. Additionally make sure thatthe sensor cables forthe FCGS andthe float switches, which go intoorthrough the tank have not been disturbed. These cables must notcontact adjacent structure and any loose or broken clips must be replaced (referto 20·09·12, pb201),
2. Notes (1) Any alterations or modifications impacting a COCCL are considered major design changes and require approval by the European Aviation Safety Agency (EASA) or by the responsible local regulatory authority under whose jurisdiction the National Type Certificate is issued. (2) 

### In cases where the critical ignition source prevention features of a component are designated, any test equipment or tooling utilized to repair or overhaul the component must be in accordance with the CMM.



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